EP 0155444 B1 19880817 - HELICOPTER ROTOR
Title (en)
HELICOPTER ROTOR
Publication
Application
Priority
US 59098784 A 19840319
Abstract (en)
[origin: EP0155444A1] A nodalized rotor system is provided for a multi-bladed helicopter. Equally spaced radial arms (20,22,24,26) each have an inboard flapping section (30) to accommodate beam-wise blade flapping and an outboard flex section (32) to accommodate pitch changes. A blade is coupled to the end of each arm with a cuff (58) and pitch horn (82) rigidly connected to the blade and pivotally connected to its arm in the region of the flapping section. The blade has a concentration of weight over the section of blade extending from about 32% to 42% of the hub-blade radius of running weight four times the running weight at 50% of the hub-blade radius. Said blade has a reduced mass at outboard 30% of the hub-blade radius, at a level of 80% of the running weight at 50% of the hub-blade radius.
IPC 1-7
IPC 8 full level
B64C 27/33 (2006.01); B64C 27/473 (2006.01); B64C 27/51 (2006.01)
CPC (source: EP US)
B64C 27/33 (2013.01 - EP US); B64C 27/473 (2013.01 - EP US)
Designated contracting state (EPC)
DE FR GB IT
DOCDB simple family (publication)
EP 0155444 A1 19850925; EP 0155444 B1 19880817; CA 1246041 A 19881206; DE 3564411 D1 19880922; JP S60215497 A 19851028; US 4601639 A 19860722
DOCDB simple family (application)
EP 85100134 A 19850108; CA 473059 A 19850129; DE 3564411 T 19850108; JP 5352885 A 19850319; US 59098784 A 19840319